Missile launcher assembly



Sept. 1, 1964 Filed Nov. 27, 1962 E. T. SUYDAM 3,146,670

MISSILE LAUNCHER ASSEMBLY 2 Sheets-Sheet 1 Edmond T. Suydam,

INVENTOR.

BY ,q-KJW Sept. 1, 1964 Filed Nov. 27, 1962 E. T. SUYDAM MISSILELAUNCHER ASSEMBLY I x l lmhh F IG. 4

2 Sheets-Sheet 2 Edmond T. Suydom,

INVENTOR.

United States Patent 3,146,67 MISSILE LAUNCHER ASSEMBLY Edmond T.Suydam, Burlington, Vt., assignor, by mesne assignments, to the UnitedStates of America as represented by the Secretary of the Army Filed Nov.27, 1962, Ser. No. 240,464 7 Claims. (Cl. 891.7)

The present invention pertains to launchers for rockets and moreparticularly relates to a jettisonable launcher assembly fitting forengaging the guide rail of the launcher.

In the use of prior launch fittings, the fitting was not jettisonableand therefor added additional weight to the missile cutting down therange for the same. Further the aerodynamic drag of the launchfittingnot only decreased the range but it caused an unbalanced torqueon the missile which affected the trajectory of the missile. In somecases an additional launch fitting was placed in the opposite side ofthe missile to balance the aerodynamic drag. This practice further addedto the weight and drag affecting the missile flight.

An object of the present invention is to provide a missile launcherassembly which employs a jettisonable launch fitting to reduce themissile weight during flight.

Another object of the invention is to provide a missile launcherassembly wherein the launch fitting is jettisonable from the missileduring the launching to reduce aerodynamic drag and unbalanced torque onthe missile during flight.

One of the important features of the invention is to provide a launcherassembly which employs a launch fitting to accurately guide the missileon the launcher rails and which is subsequently positively andmechanically separated from the missile at the terminal end of thelauncher rail.

These and other objects and advantages of the present invention willbecome apparent from the following detailed description taken with theaccompanying drawings, wherein:

FIGURE 1 is a fragmentary side elevation view partially broken awayillustrating the missile launcher assembly of the present invention.

FIGURE 2 is a fragmentary bottom view of the launch er along line 22 ofFIGURE 1;

FIGURE 3 is a sectional view taken on line 33 of FIGURE 1; and

FIGURE 4 is a perspective view of the launch fitting.

Referring now to the drawings and particularly to FIGURE 1 thereof,indicates a missile on a launcher 12 adjacent the end of its travel onthe launcher. Launcher rail 14 is broken away to illustrate ajettisonable fitting 16 which forms an important part of the launcherassembly of the present invention. Fitting 16 is illustrated in phantomat two further positions 16a and 1612 representing the positions of thefitting at later periods during the launching process, and illustratingthe manner of separation of the fitting from the missile.

Fitting 16 is in the form of a pin or shank portion 18 (FIGURE 4) havinga rectangular head 20, the sides of which define guide faces. A J-slot22 is formed in pin 18 at the distal end thereof. Head 20 is providedwith a cam surface 24 which is inclined with respect to the axis of thepin for purposes explained hereinbelow.

A spacer ring 25 is mounted on pin 18, for purposes describedhereinbelow, by a retaining pin 26 which is fixed in a radial bore inring 25 and projects inwardly therefrom into a vertical slot 28 formedin pin 18. Thus ring 25 is capable of limited movement longitudinally ofpin 18 but is precluded from removal from the pin.

The skin 30 of missile 10 (FIGURE 3) is provided with internal bosses 32at points adapted to be adjacent rails 14 of the launcher. Each boss 32is provided with "ice a blind bore 34 which is radial of the missile andleads tot the exterior thereof. A shear pin 36 extends radially throughthe wall of boss 32 and projects into blind bore 34 for engagement withJ-slot 22 on fitting 16. When the missile is to be launched, launchfitting 16 is inserted into blind bore 34 so that shear pin 36 engagesJ-slot 22. A degree turn of the fitting then seats shear pin 36 in thebottom of J-slot 22 and locks the fitting in place.

The guide rail 14 is generally U-shaped in cross section, as best seenin FIGURE 3, and comprises a bottom 40, two sides 42 and 44, and twoinwardly projecting top plates 46 and 48 at the upper edges of sideplates 42 and 44, respectively. When the rectangular head 26 of launchfitting 16 is inserted within side rail 14 it cannot turn and thus thefitting cannot disengage itself from the missile.

The previously mentioned ring 25 is interposed be tween missile 10 andthe upper surfaces of top plates 46 and 48 to prevent damage to themissile skin by rubbing on the rail surface, and to provide clearancebetween the missile and the rail to prevent tilting of the missile whenthe center of gravity thereof passes the end of the launcher rail andbefore the rear end of the missile leaves the rail. The clearance alsopermits movement of the missile due to crosswind without causing tiltingof the missile.

As best seen in FIGURES 1 and 2, bottom plate 40 of guide rail 14 is cutaway at 50 adjacent the terminal end of the guide rail. Two fittingretracting plates 52 and 54 v are fastened to the inner surfaces of sideplates 42 and 44, respectively, of guide rail 14 by capscrews 55. Thelower edges of retraction plates 52 and 54 are inclined downwardly andforwardly from guide rail 14 at substantially the same angle as camsurface 24 on head 20 of launch fitting 16.

When the missile approaches the terminal ends of rails 14, the camsurfaces 24 on head 20 of launch fitting 18 contact the under side ofretraction plates 52 and 54. Further forward movement of the missilecauses the launch fitting to be withdrawn from the missile, asillustrated in phantom at 16a (FIGURE 1) shearing pin 36. When thelaunch fitting reaches the ends of plates 52 and 54 it drops to theground, as illustrated at 16b, and can then be reused to launch anothermissile.

While a preferred embodiment of the invention has been described hereinit should be noted that various changes may be made therein withoutdeparting from the spirit of the invention as defined in the appendedclaims.

I claim:

1. In a missile launcher assembly the combination which comprises, amissile, a U-shaped guide rail, a launch fitting releasably mounted in alateral bore in said missile, said fitting having a rectangular head forengagement within said guide rail, a pair of retraction plates fixed tothe side sections of said U-shaped guide rail adjacent the forward endthereof, said retraction plates projecting forwardly and downwardly fromsaid guide rail, and inclined cam surfaces formed on the head of saidlaunch fitting for engagement with said retraction plates, whereby asthe missile moves forward on said guide rail the retraction plates willengage said launch fitting and withdraw said fitting from said missile.

2. A missile launcher assembly as set forth in claim 1 wherein a shearpin is mounted in said missile and projects into said lateral bore, anda J-slot is formed in said fitting for engagement with said shear pin.

3. A missile launcher assembly as set forth in claim 1, wherein a spacerring is mounted on said fitting between said missile and said launcherrail.

4. A missile launcher assembly as set forth in claim 3 wherein saidspacer ring is mounted for limited movement with respect to said fittingby a pin radially affixed to said ring and projecting inwardly into alongitudinal groove formed in said fitting.

5. For use in a missile launcher assembly the combination whichcomprises, a missile having a lateral bore formed therein, a shear pinprojecting into said bore, a launch fitting having a shank portion and ahead, said shank portion being received in said bore, a J-slot formed insaid shank portion of said fitting, said shear pin being received insaid J-slot so as to latch said shank portion in said bore, and saidhead having cam surface means and flat guide faces for coaction withmeans on a guide rail to adapt said fitting for removal from said boreby sufiicient force being applied to said cam surface means so as tocause shearing of said shear pin.

6. For use in a missile launcher assembly, the combination whichcomprises, a missile having a lateral bore formed therein, a shear pinprojecting into said bore, a launch fitting having a shank portion and arectangular head portion, said shank portion being received in saidReferences Cited in the file of this patent UNITED STATES PATENTS2,397,572 Weaver Apr. 2, 1946 2,771,811 Lauritsen Nov. 27, 19562,826,960 Schiavi Mar. 18, 1958 2,962,934 Seidner Dec. 6, 1960 3,017,835Holtz Jan. 23, 1962 3,038,382 Noyes et al June 12, 1962

1. IN A MISSILE LAUNCHER ASSEMBLY THE COMBINATION WHICH COMPRISES, AMISSILE, A U-SHAPED GUIDE RAIL, A LAUNCH FITTING RELEASABLY MOUNTED IN ALATERAL BORE IN SAID MISSILE, SAID FITTING HAVING A RECTANGULAR HEAD FORENGAGEMENT WITHIN SAID GUIDE RAIL, A PAIR OF RETRACTION PLATES FIXED TOTHE SIDE SECTIONS OF SAID U-SHAPED GUIDE RAIL ADJACENT THE FORWARD ENDTHEREOF, SAID RETRACTION PLATES PROJECTING FORWARDLY AND DOWNWARDLY FROMSAID GUIDE RAIL, AND INCLINED CAM SURFACES FORMED ON THE HEAD OF SAIDLAUNCH FITTING FOR ENGAGEMENT WITH SAID RETRACTION PLATES, WHEREBY ASTHE MISSILE MOVES FORWARD ON SAID GUIDE RAIL THE RETRACTION PLATES WILLENGAGE SAID LAUNCH FITTING AND WITHDRAW SAID FITTING FROM SAID MISSILE.